The present application provides a cooling system for a gas turbine. The cooling system may include a source of CO2, a stator blade cooling system positioned about a casing of the gas turbine and in communication with the source of CO2 and a number of stator blades, and a rotor blade cooling system positioned about a rotor shaft of the gas turbine and in communication with the source of CO2 and a number of rotor blades. A first portion of a flow of CO2 may flow through the stator blade cooling system and returns to the source of CO2 in a first closed loop and a second portion of the flow of CO2 may flow through the rotor blade cooling system and returns to the source of CO2 in a second closed loop.
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1. A cooling system for a gas turbine, comprising:
a source of CO2;
a stator blade cooling system positioned about a casing of the gas turbine and in communication with the source of CO2 and a plurality of stator blades; and
a rotor blade cooling system positioned about a rotor shaft of the gas turbine and in communication with the source of CO2 and a plurality of rotor blades;
wherein a first portion of a flow of CO2 flows through the stator blade cooling system and returns to the source of CO2 in a first closed loop and wherein a second portion of the flow of CO2 flows through the rotor blade cooling system and returns to the source of CO2 in a second closed loop.
15. A cooling system for a gas turbine, comprising:
a source of CO2;
a stator blade cooling system positioned about a casing of the gas turbine and in communication with the source of CO2 and a plurality of stator blades;
wherein the plurality of stator blades comprises an internal stator plenum; and
a rotor blade cooling system positioned axially through a rotor shaft of the gas turbine and in communication with the source of CO2 and a plurality of rotor blades;
wherein the plurality of rotor blades comprises an internal rotor plenum;
wherein a first portion of a flow of CO2 flows through the stator blade cooling system and returns to the source of CO2 in a first closed loop and wherein a second portion of the flow of CO2 flows through the rotor blade cooling system and returns to the source of CO2 in a second closed loop.
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The present application is a continuation-in-part of U.S. Ser. No. 12/729,745, entitled “System and Method for Cooling Gas Turbine Components”, filed on Mar. 23, 2010, now pending.
The subject matter disclosed herein relates to gas turbines and, more particularly, to cooling mechanisms in gas turbines.
Integrated Gasification Combined Cycle (IGCC) systems are increasingly being utilized for power generation. IGCC systems use a gasification process to produce a synthesis gas (syngas) from fuel sources such as coal, heavy petroleum residues, biomass and others. The syngas is used as a fuel in gas turbines for producing electricity. IGCC systems can be advantageous in reducing carbon dioxide (CO2) emissions through mechanisms such as pre-combustion carbon capture.
IGCC power plants adopt pre-combustion systems for CO2 capture. Currently, the capture of CO2 from IGCC plants penalizes the performance of such plants, particularly in production output and efficiency. In addition, cooling of the stationary and rotating components of a gas turbine by the conventional method of extracting air from the compressor reduces turbine efficiency by, for example, reducing the Brayton cycle efficiency. This loss of efficiency is manifested due to factors such as a reduction in firing temperatures due to non-chargeable flow diluting the combustor exit temperature, a reduction in work on account of bypassing compressed air at upstream stages of the turbine, and a reduction in work potential on account of dilution effects of the coolant stream mixing in the main gas path and the associated loss of aerodynamic efficiency.
The present application and the resultant patent thus provide a cooling system for a gas turbine. The cooling system may include a source of CO2, a stator blade cooling system positioned about a casing of the gas turbine and in communication with the source of CO2 and a number of stator blades, and a rotor blade cooling system positioned about a rotor shaft of the gas turbine and in communication with the source of CO2 and a number of rotor blades. A first portion of a flow of CO2 may flow through the stator blade cooling system and return to the source of CO2 in a first closed loop and a second portion of the flow of CO2 may flow through the rotor blade cooling system and return to the source of CO2 in a second closed loop.
The present application and the resultant patent further provide a method of cooling a number of blades in a gas turbine. The method may include the steps of generating a flow of CO2 in a cooling system, flowing a portion of the CO2 through the blade so as to cool the blade and transfer heat to the flow of CO2, flowing the heated CO2 through a heat exchanger, and returning the portion of the flow of CO2 to the cooling system.
The present application and the resultant patent further provide a cooling system for a gas turbine. The cooling system may include a source of CO2, a stator blade cooling system positioned about a casing of the gas turbine and in communication with the source of CO2 and a number of stator blades with an internal stator plenums, and a rotor blade cooling system positioned axially through a rotor shaft of the gas turbine and in communication with the source of CO2 and a number of rotor blades with internal rotor plenums. A first portion of a flow of CO2 flows through the stator blade cooling system and returns to the source of CO2 in a first closed loop and a second portion of the flow of CO2 flows through the rotor blade cooling system and returns to the source of CO2 in a second closed loop.
These and other advantages and features will become more apparent from the following description taken in conjunction with the drawings.
The subject matter, which is regarded as the invention, is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features, and advantages of the present application are apparent from the following detailed description taken in conjunction with the accompanying drawings in which:
There is provided a system and method for improving the output and efficiency of turbine systems that utilize gasification to supply turbine combustion fuel. An exemplary turbine system includes integrated gasification combined cycle (IGCC) power generation systems. In one example, the systems and method are utilized in conjunction with IGCC or other turbine systems that incorporate pre-combustion systems for carbon dioxide (CO2) capture. Exemplary systems and methods include cooling turbines using CO2 captured by a power generation and/or CO2 removal system. Exemplary systems and methods utilize captured CO2 as cooling media for cooling of stationary and/or rotating components of turbines, such as gas turbines, in a closed loop cooling scheme.
With reference to
The turbine includes various internal components that are exposed to elevated temperatures during operation of the turbine assembly 10. Such components include a rotor shaft and rotor disks that rotate about a central axis. Exemplary components also include rotating components 24 such as blades or buckets, which can be removably attached to an outer periphery of each rotor disk. Other components include stationary components 26 such as stator vanes or nozzles.
In one example, referring to
In one example, the combustion chamber 18, or other suitable equipment, is utilized in an oxyfuel cycle. Oxyfuel cycles generally include the combustion of fuel with pure oxygen, in place of air. Oxyfuel includes an oxygen enriched gas mixture diluted with combustion gas such as gas turbine exhaust (i.e., a flue gas including mostly of CO2 and H2O).
The gases, in one example, are advanced into a two stage shift reactor 34 in which water vapor is used to convert the CO into carbon dioxide (CO2). At this stage, the syngas is a raw syngas that includes acid gases, which include various contaminants such as CO2 and hydrogen sulfide (H2S). Various other gases also are produced in the gasification process, and present in the syngas, such as nitrogen, carbon monoxide, and others.
An acid gas removal (AGR) plant 42 then receives the raw syngas. The AGR plant 42 processes the raw syngas to remove H2S, which can be sent to a tail gas treatment unit (TGTU) 40, and CO2 from the raw syngas. The AGR plant 42 includes, for example, an absorber in which a solvent absorbs H2S and CO2 from the raw syngas to produce a “sweetened” or clean syngas. An example of a suitable solvent is Selexol™ (Union Carbide Corporation), although any solvent capable of removing acid gases from a gas mixture may be used. In addition to solvent-based processes, the AGR plant 42 may use any suitable process for sweetening the syngas. Examples of such sweetening processes include selective gas removal processes such as the utilization of CO2 and H2S selective membranes, warm sulphur removal technologies and others.
In one example, after the syngas is cleaned, the solvent includes concentrations of H2S and CO2 and may be referred to as a “rich” solvent. The rich solvent is fed into one or more regenerators (including, for example, a stripper and boiler) in which the H2S and CO2 are stripped from the solvent, resulting in a “lean” solvent. The lean solvent can be recycled for use in subsequent acid gas removal operations.
In one example, the removed CO2 is advanced through an Integrated CO2 Enrichment system 44, and sent to a compression and/or storage unit 46 for CO2 capture and/or enhanced oil recovery. A portion of the CO2, in one example, is diverted via a recycling/compression system 38 and directed back into the gasification unit 32. In addition, the TGTU 40 may be used to remove sulphur from the raw syngas.
The clean syngas is then advanced through various saturation and heating systems 48 and fed into a combined cycle power block 50 for power generation. The power block 50 includes a gas turbine such as the gas turbine assembly 10 and may also include a steam turbine for producing energy from the gas turbine exhaust gases.
In one example, the IGCC plant 30 includes an air separation unit (ASU) 52. Air can be diverted from the gas turbine compressor and fed into the ASU 52. The ASU 52 separates oxygen from the air that can be fed into the gasification unit 32, and also produces nitrogen, which can be diverted back to the turbine for cooling.
In one example, a portion of the CO2 at a suitable pressure is extracted from the CO2 removal system and diverted to the power block 50 to cool the gas turbine stationary or rotating components in a closed loop system wherein the heat picked up by CO2 is recovered. The CO2 is diverted to the gas turbine via any suitable cooling system 54. In one example, the cooling system 54, the combined cycle power block 50 and/or the IGCC power plant 30 includes one or more heat exchangers to regenerate thermal energy from the CO2 that has been heated as a result of applying the CO2 to the gas turbine. The heat exchanges are configured to heat components such as the fuel and/or diluent stream entering the gas turbine, the steam turbine, as well as any other desired fluids such as boiler fluids. After the CO2 is applied to the gas turbine and/or the steam turbine, and any additional components, it may be subsequently sent to the compression and/or storage system 46, where the CO2 is compressed to a selected pressure, such as 2000 psig (˜about 140 bars), a typical pressure to supply liquid CO2 for Enhanced Oil Recovery (EOR) applications.
Referring to
In one example, the cooling system 60 is in operable communication with the gas turbine 64 and a portion of the AGR plant 42. The AGR plant 42 includes one or more flash tanks 68 that separate CO2 from a rich solvent. Gas conduits 69 are configured to route the separated CO2 from the flash tanks 68 to desired locations, such as the compression and/or storage unit 46. In one example, CO2 fluid from a H2S reabsorber 67 is routed to the gas turbine cooling CO2 controller 66. The cooling system conduits 62 are in fluid communication with respective gas conduits 69 to divert a portion of the separated CO2 into the cooling system 60. The flow of CO2 into the cooling system can be controlled by the controller 66. In one example, the cooling system 60 includes valves 70 for controlling the flow of CO2 from the gas conduits 69, through the cooling system 60 and into the gas turbine 64. The valves 70 may be selectively operated via, for example, the controller 66.
The cooling system 60, in one example, is a closed loop system. For example, as shown in
Another example of the cooling system 60 is shown in reference to
In this example, CO2 fluid from the ICU is fed to the heat exchangers 82 that are configured to transfer heat from the bleed CO2 to fluids such as the fuel, diluent, compressor discharge air and/or boiler feed water (BFW). Further heat is transferred back to the CO2 which is entering ICU through a regenerative heat exchanger system 84 CO2 fluid can also be cooled through optional low temperature heat exchange systems 94 (e.g., trim coolers, other areas of steam heat exchangers and others) that further cool the CO2 to facilitate compression, liquefaction and/or sequestration. Lastly, the cooled CO2 is diverted to the compression and sequestration unit 90.
In one example, the cooling system 60 is in fluid communication with a CO2 capture, recovery and sequestration system 86. The CO2 capture unit includes a number of capture modules 88. Exemplary capture modules include flash tanks 68 through which the rich solvent is passed. The capture modules 88 can include high pressure (HP), medium pressure (MP) and/or low pressure (LP) modules 88 in fluid communication with a CO2 compression and sequestration unit 90. In use, a portion of the CO2 from the capture modules 88 may be diverted through an optional gas compression system 92 through regenerative heat exchangers 84 to selected ICU of turbine components.
In the first stage 101, the fuel is flowed into a gasification system such as the gasification and scrubbing unit 32 and raw syngas is produced. The raw syngas is cleaned or sweetened by a suitable cleaning system such as the AGR plant 42 to remove acid gases from the raw syngas.
In the second stage 102, CO2 gas is extracted from the raw syngas and/or from byproducts of cleaning the raw syngas. For example, CO2 gas is removed from a solvent used to clean the raw syngas by the flash tanks 68 or other CO2 extraction mechanisms. The CO2 gas is advanced to a CO2 capture and/or storage system, such as the compression and/or storage unit 46.
In the third stage 103, a portion of the CO2 gas is diverted to a cooling system such as the cooling system 60 that applies the CO2 gas portion to selected components of a turbine such as a gas turbine. Exemplary components include rotating blades or buckets and stationary components such as stator vanes.
In the fourth stage 104, the CO2 gas portion, which has been heated by the turbine components, is recovered in thermal energy, regenerated and then returned to the CO2 capture and/or storage system. In one example, the heated CO2 gas portion is cooled and the thermal energy is transferred to fuel, diluents and/or other components of a power generation system prior to returning the CO2 gas portion to the CO2 capture and/or storage system. In one example, the CO2 gas portion is cooled by transferring thermal energy from the CO2 gas portion to an indirect cooling unit by a suitable heat exchange mechanism such as the regenerative heat exchanger 84.
As described above, the cooling system 60 may flow a portion of the CO2 gas into the power turbine stage 72 so as to cool the moving components and/or the stationary components therein.
The stator blade cooling system 110 may include a stator coolant inlet pipe 140 that may be in communication with the cooling system 60 and the flow of CO2. A number of stator coolant inlet pipes 140 may be used herein. The stator coolant inlet pipes 140 may be in communication with a stator coolant inlet plenum 150. The stator coolant inlet plenum 150 may encircle the casing 130 in whole or in part. The stator coolant inlet plenum 150 may be in communication with some or all of the stator blades 120 via a number of stator blade cooling inflow lines 160. Other components and other configurations may be used herein.
As is shown in
Referring again to
The rotor blade cooling system 250 may include a rotor coolant inlet pipe 290. The rotor coolant inlet pipe 290 may be in communication with the cooling system 60 and the flow of CO2. The rotor coolant inlet pipe 290 may extend axially through the rotor disk 270 of the rotor shaft 280 and then radially to a rotor coolant inlet plenum 300. The rotor coolant inlet plenum 300 may encircle the rotor disk 270 in whole or in part. Other components and other configurations may be used herein.
The rotor coolant inlet plenum 300 may be in communication with some or all of the rotor blades 260 via a number of rotor blade cooling inflow lines 310. Referring again to
Referring again to
The cooling system 60 thus may be in communication with the stator blade cooling system 110 and the rotor blade cooling system 250 so as to adequately cool the stator blades 120 and the rotor blades 260 in a first closed loop configuration and a second closed loop configuration. The heat generated by the turbine components and the thermal energy therein may be transferred to fuel, diluents, and/or other components of the overall system before returning the CO2 flow. The stator blade cooling system 110 and the rotor blade cooling system 250 thus cool the components herein with the flow of CO2 instead of a parasitic flow of air from the compressor or elsewhere.
It should be apparent that the foregoing relates only to certain embodiments of the present application and the resultant patent. Numerous changes and modifications may be made herein by one of ordinary skill in the art without departing from the general spirit and scope of the invention as defined by the following claims and the equivalents thereof.
Anand, Ashok Kumar, Muthuramalingam, Mahendhra, Muthaiah, Veerappan
Patent | Priority | Assignee | Title |
10316750, | Feb 21 2014 | Rolls-Royce North American Technologies, Inc.; Rolls-Royce Corporation | Single phase micro/mini channel heat exchangers for gas turbine intercooling |
10371053, | Feb 21 2014 | Rolls-Royce North American Technologies, Inc.; Rolls-Royce Corporation | Microchannel heat exchangers for gas turbine intercooling and condensing |
11208954, | Feb 21 2014 | Rolls-Royce Corporation; Rolls-Royce North American Technologies, Inc. | Microchannel heat exchangers for gas turbine intercooling and condensing |
Patent | Priority | Assignee | Title |
4190398, | Jun 03 1977 | General Electric Company | Gas turbine engine and means for cooling same |
5428950, | Nov 04 1993 | General Electric Company | Steam cycle for combined cycle with steam cooled gas turbine |
5577377, | Nov 04 1993 | General Electric Company | Combined cycle with steam cooled gas turbine |
5611197, | Oct 23 1995 | General Electric Company | Closed-circuit air cooled turbine |
5613356, | Mar 21 1994 | Alstom Technology Ltd | Method of cooling thermally loaded components of a gas turbine group |
5724805, | Aug 21 1995 | UNIVERSITY OF MASSASCHUSETTS-LOWELL | Power plant with carbon dioxide capture and zero pollutant emissions |
5865598, | Jul 02 1997 | SIEMENS ENERGY, INC | Hot spot detection system for vanes or blades of a combustion turbine |
5960249, | Mar 06 1998 | General Electric Company | Method of forming high-temperature components and components formed thereby |
6066824, | Apr 20 1998 | Michigan Technological University | Resistance welding system with a self-contained close-loop cooling arrangement |
6197424, | Mar 27 1998 | SIEMENS ENERGY, INC | Use of high temperature insulation for ceramic matrix composites in gas turbines |
6253554, | Sep 18 1997 | Kabushiki Kaisha Toshiba | Gas turbine plant with fuel heating and turbine cooling features |
6295803, | Oct 28 1999 | SIEMENS ENERGY, INC | Gas turbine cooling system |
6339926, | Nov 20 1998 | MITSUBISHI HITACHI POWER SYSTEMS, LTD | Steam-cooled gas turbine combined power plant |
6398503, | Apr 27 1998 | Kabushiki Kaisha Toshiba | High temperature component, gas turbine high temperature component and manufacturing method thereof |
6487863, | Mar 30 2001 | SIEMENS ENERGY, INC | Method and apparatus for cooling high temperature components in a gas turbine |
6506013, | Apr 28 2000 | General Electric Company | Film cooling for a closed loop cooled airfoil |
6672075, | Jul 18 2002 | University of Maryland | Liquid cooling system for gas turbines |
6684653, | Nov 21 2001 | Air-conditioner and air-to-air heat exchange for closed loop cooling | |
6988367, | Apr 20 2004 | WILLIAMS INTERNATIONAL CO L L C | Gas turbine engine cooling system and method |
7178339, | Apr 07 2004 | Lockheed Martin Corporation | Closed-loop cooling system for a hydrogen/oxygen based combustor |
7359198, | Sep 29 2005 | AVAGO TECHNOLOGIES GENERAL IP SINGAPORE PTE LTD | System and method for inducing turbulence in fluid for dissipating thermal energy of electronic circuitry |
7892324, | Oct 10 2007 | Air Products and Chemicals, Inc | Systems and methods for carbon dioxide capture |
8171718, | Oct 05 2009 | General Electric Company | Methods and systems involving carbon sequestration and engines |
8438874, | Jan 23 2008 | Hitachi, LTD | Natural gas liquefaction plant and motive power supply equipment for same |
20030094006, | |||
20040224210, | |||
20050223711, | |||
20060032228, | |||
20070006592, | |||
20070125063, | |||
20070199300, | |||
20070234729, | |||
20070242434, | |||
20070245749, | |||
20090149930, | |||
20100018216, | |||
20100275644, | |||
20110020188, | |||
20110232298, | |||
20110260113, | |||
20110277981, | |||
20110314819, | |||
20112011102, | |||
20120174621, | |||
20130086883, | |||
20130125555, | |||
20130229018, | |||
20140020359, | |||
20140020402, | |||
20140030073, | |||
EP709885, | |||
EP990800, | |||
GB2433581, | |||
RE36497, | Nov 04 1993 | General Electric Co. | Combined cycle with steam cooled gas turbine |
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